### 26484 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules

30 CEE High Efficiency Residential Swimming Pool Initiative, Consortium of Energy Efficiency.
Available at http://library.cee1.org/sites/default/ files/library/9986/cee

_res

_swimmingpoolinitiative

_ 07dec2012

_ pdf

_ 10557.pdf

. 31 Size standards, listed by NAICS code and industry description and are available at http:// www.sba.gov/category/navigation-structure/contracting/contracting-officials/smallbusinesssize-standards

. Issue 28: DOE seeks comment regarding the typical energy use of dedicated-purpose pool pumps. If available, DOE requests that these data be broken-out by equipment type, hp (rated nameplate hp or THP), operating speed, application, and any other parameters relevant to the pool pump industry.

Issue 29: A study by CEE 30 estimates that adopting higher efficiency technologies, such as multi-speed and variable-speed pool pumps, may result in energy savings of 1,900–3,800 kWh/ year for each residential swimming pool pump. DOE seeks comment on whether the approach and assumptions described in that report would be appropriate to use as a basis for estimating national energy savings, and on the accuracy of the estimates themselves. If so, why? If not, why not?

Issue 30: The pool pump industry defines ‘‘turnover rate’’ as the total number of times the entire volume of water in the pool is circulated (or ‘‘turned over’’) within a 24-hour period. The industry defines ‘‘turnover time’’ as the amount of time required to circulate the entire volume of water in the pool once. Turnover rate is calculated by dividing 24 hours by the turnover time in hours. DOE seeks comment on typical turnover rates and times, as well as any variation by application, state, or climate region.

Issue 31: DOE seeks comment on the usage profiles of dedicated-purpose pool pumps broken-out by climate, pool or pump type (i.e., inground or aboveground, indoor or outdoor), hp (rated nameplate hp or THP), and efficiency. DOE is specifically interested in hours of use per day at each speed when multi-speed or variable-speed pumps are used.

Issue 32: DOE seeks data and comment on the number of months per year that dedicated-purpose pool pumps typically operate, broken-out by state or climate region.

Issue 33: DOE requests comment onthe typical lifetime of dedicatedpurpose pool pumps.

3. Manufacturer Impact Analysis

Issue 34: DOE seeks to identify all dedicated-purpose pool pump manufacturers that currently distribute equipment in the United States. Currently, DOE has identified Pentair Ltd., Hayward Industries, Inc., Zodiac, Speck Pumps, and Waterway Plastics as dedicated-purpose pool pump manufacturers. DOE seeks comment on the comprehensiveness of this list of manufacturers, and requests the names and contact information of any other domestically- or foreign-based manufacturers that sell or otherwise market their dedicated-purpose pool pumps in the United States.

Issue 35: DOE seeks to identify all dedicated-purpose pool pump manufacturers that currently distribute equipment in the United States who also qualify as small businesses. The Small Business Administration (SBA) defines a small business under North American Industry Classification System (NAICS) code 333911, ‘‘Pump and Pumping Equipment Manufacturing,’’ as one having no more than 500 employees. 31 DOE requests the names of any small business manufacturers of dedicated-purpose pool pumps that it should consider in its analysis.

III. Public Participation

DOE will accept comments, data, and information regarding this RFI and other matters relevant to DOE’s consideration of any energy conservation standards for dedicated-purpose pool pumps by June 22, 2015. After the close of the comment period, DOE will begin collecting data, conducting the analyses, and reviewing the public comments. These actions will be taken to aid in the consideration of a rulemaking for dedicated-purpose pool pumps.

Instructions: All submissions received must include the agency name and docket number and/or RIN for this rulemaking. No telefacsimilies (faxes) will be accepted.

Docket: The docket is available for
review at www.regulations.gov, including Federal Register notices, public meeting attendees’ lists and transcripts, comments, and other supporting documents/materials. All documents in the docket are listed in the www.regulations.gov index. However, not all documents listed in the index may be publicly available, such as information that is exempt from public disclosure.

A link to the docket Web page can be found at: http://www.regulations.gov/#!docketDetail;D=EERE-2015-BT-STD0008. This Web page contains a link to the docket for this notice on the www.regulations.gov Web site. The www.regulations.gov Web page contains simple instructions on how to access all documents, including public comments, in the docket.

For information on how to submit a comment, or review other public comments and the docket, contact Ms. Brenda Edwards at (202) 586–2945 or by email: Brenda.Edwards@ee.doe.gov.

DOE considers public participation to be a very important part of the process for developing test procedures. DOE actively encourages the participation and interaction of the public during the comment period in each stage of the rulemaking process. Interactions with and between members of the public provide a balanced discussion of the issues and assist DOE in the rulemaking process. Anyone who wishes to be added to the DOE mailing list to receive future notices and information about this rulemaking should contact Ms. Brenda Edwards at (202) 586–2945, or via email at Brenda.Edwards@ ee.doe.gov.

Issued in Washington, DC, on April 24,

2015. Kathleen Hogan, Deputy Assistant Secretary for Energy Efficiency, Energy Efficiency and Renewable Energy.

[FR Doc. 2015–11011 Filed 5–7–15; 8:45 am]

**BILLING CODE 6450–01–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–1279; Directorate Identifier 2014–NM–049–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; BAE SYSTEMS (Operations) Limited**  **Airplanes**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to supersede Airworthiness Directive (AD) 2011–21– 06 for all BAE SYSTEMS (Operations) Limited Model 4101 airplanes. AD 2011–21–06 currently requires revising the maintenance program. Since we issued AD 2011–21–06, we have determined that the life limit of certain main landing gear components must be reduced, and certain post-repair inspections of critical structure are necessary. This proposed AD would require a new revision of the maintenance/inspection program. We are proposing this AD to prevent failure of certain structurally significant items,


### 26485 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules

including the main landing gear and nose landing gear, which could result in reduced structural integrity of the airplane; and to prevent fuel vapor ignition sources, which could result in a fuel tank explosion and consequent loss of the airplane.

**DATES :**  We must receive comments on this proposed AD by June 22, 2015.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact BAE SYSTEMS (Operations) Limited, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email RApublications@baesystems.com;

Internet http://www.baesystems.com/ Businesses/RegionalAircraft/index.htm. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 1279; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1175; fax 425–227–1149. **SUPPLEMENTARY INFORMATION :** 

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2015–1279; Directorate Identifier 2014–NM–049–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

On September 23, 2011, we issued AD 2011–21–06, Amendment 39–16829 (76 FR 64788, October 19, 2011). AD 2011– 21–06 requires actions intended to address an unsafe condition on BAE SYSTEMS (Operations) Limited Model 4101 airplanes.

Since we issued AD 2011–21–06, Amendment 39–16829 (76 FR 64788, October 19, 2011), we have determined that the life limit of certain main landing gear components must be reduced, and new inspections of certain repairs that affect fatigue strength of critical structure must be added to the maintenance/inspection program.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0043, dated February 21, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

The Jetstream J41 Aircraft Maintenance Manual (AMM), includes the following chapters:

05–10–10 ‘‘Airworthiness Limitations’’,
05–10–20 ‘‘Certification Maintenance Requirements’’, and,

05–10–30 ‘‘Critical Design Configuration Control Limitations (CDCCL)—Fuel System’’.

The maintenance tasks and limitations contained in these chapters have been identified as mandatory actions for continued
airworthiness and EASA issued AD 2010– 0098 [dated May 27, 2010 (http:// ad.easa.europa.eu/ad/2010-0098 ) which corresponds to FAA AD 2011–21–06, Amendment 39–16829 (79 FR 64788, October 19, 2011)] to require operators to comply
with those instructions. Since that [EASA] AD was issued, BAE Systems (Operations) Ltd issued Revision 37 of the AMM amending Chapter 05–10–10 to revise and reduce the life limit of certain main landing gear components. In addition, Revision 38 of the AMM was issued to amend Chapters 05–10–00 and 05–10–10 introducing inspections to be accomplished after implementation of some repairs affecting fatigue strength of critical structure. Failure to comply with the new and more restrictive actions could result in an unsafe condition.

For the reasons described above, this [EASA] AD, which supersedes EASA AD 2010–0098, requires implementation of the maintenance requirements and/or airworthiness limitations as specified in the defined parts of Chapter 05 of the AMM at
Revision 38.

The unsafe condition is the failure of certain structurally significant items, including the main landing gear and nose landing gear, which could result in reduced structural integrity of the airplane; and fuel vapor ignition sources, which could result in a fuel tank explosion and consequent loss of the airplane. You may examine the MCAI in the AD docket on the Internet

at http://www.regulations.gov by searching for and locating Docket No.

FAA–2015–1279.

Related Service Information Under 1
CFR Part 51

BAE SYSTEMS (Operations) Limited has issued Subjects 05–10–10, ‘‘Airworthiness Limitations’’; 05–10–20, ‘‘Certification Maintenance Requirements’’; and 05–10–30, ‘‘Critical Design Configuration Control Limitations (CDCCL)—Fuel System’’; of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited J41 AMM, Revision 38, dated September 15, 2013, which describe procedures for inspections of structurally significant items and the fuel system. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the **ADDRESSES** section of this NPRM.

FAA’s Determination and Requirements of This Proposed AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent


### 26486 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules

information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.

Costs of Compliance

We estimate that this proposed AD affects 4 airplanes of U.S. registry.

The actions required by AD 2011–21– 06, Amendment 39–16829 (76 FR 64788, October 19, 2011), and retainedin this proposed AD take about 1 workhour per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2011– 21–06 is $85 per product.

We also estimate that it would take about 1 work-hour per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $340, or $85 per product.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority.

We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking
action.
Regulatory Findings

We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify this proposed regulation:

1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866;

2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and

4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

**PART 39—AIRWORTHINESS DIRECTIVES** 

■ 1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011–21–06, Amendment 39–16829 (76 FR 64788, October 19, 2011), and adding the following new AD:

BAE SYSTEMS (Operations) Limited: Docket No. FAA–2015–1279; Directorate Identifier 2014–NM–049–AD.

(a) Comments Due Date

We must receive comments by June 22,

2015.

(b) Affected ADs

This AD replaces AD 2011–21–06, Amendment 39–16829 (76 FR 64788, October 19, 2011).

(c) Applicability

This AD applies to all BAE SYSTEMS (Operations) Limited Model 4101 airplanes, certificated in any category.

(d) Subject

Air Transport Association (ATA) of
America Code 05.

(e) Reason

This AD was prompted by the need to reduce the life limit of certain main landinggear components, and to add certain postrepair inspections of critical structure to the maintenance/inspection program. We are issuing this AD to prevent failure of certain structurally significant items, including the main landing gear and nose landing gear,
which could result in reduced structural integrity of the airplane; and to prevent fuel vapor ignition sources, which could result in a fuel tank explosion and consequent loss of the airplane.

(f) Compliance

Comply with this AD within the compliance times specified, unless already
done. (g) Retained Maintenance Program Revision, With No Changes

This paragraph restates the requirements of paragraph (i) of AD 2011–21–06, Amendment 39–16829 (76 FR 64788, October 19, 2011), with no changes. Within 90 days after November 23, 2011 (the effective date of AD 2011–21–06): Revise the maintenance program by incorporating Subjects 05–10–10, ‘‘Airworthiness Limitations’’; 05–10–20, ‘‘Certification Maintenance Requirements’’; and 05–10–30, ‘‘Critical Design Configuration Control Limitations (CDCCL)—Fuel System’’; of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited Jetstream Series 4100 Aircraft Maintenance Manual (AMM), Revision 35, dated February 15, 2011. The initial compliance times for the tasks are at the applicable times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. Doing the actions required by paragraph (i) of this AD terminates the requirements of this paragraph.

(1) For replacement tasks of life limited parts specified in Subject 05–10–10, ‘‘Airworthiness Limitations,’’ of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited Jetstream Series 4100 AMM, Revision 35, dated February 15, 2011: Prior to the applicable flight cycles (landings) or flight hours (flying hours) on the part specified in the ‘‘Mandatory Life Limits’’ column in Subject 05–10–10, or within 90 days after November 23, 2011 (the effective date of AD 2011–21– 06, Amendment 39–16829 (76 FR 64788, October 19, 2011)), whichever occurs later.

(2) For structurally significant item tasks specified in Subject 05–10–10, ‘‘Airworthiness Limitations,’’ of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited Jetstream Series 4100 AMM, Revision 35, dated February 15, 2011: Prior to the accumulation of the applicable flight cycles specified in the ‘‘Initial Inspection’’ column in Subject 05– 10–10, or within 90 days after November 23, 2011 (the effective date of AD 2011–21–06, Amendment 39–16829 (76 FR 64788, October 19, 2011)), whichever occurs later.

(3) For certification maintenance requirements tasks specified in Subject 05– 10–20, ‘‘Certification Maintenance Requirements,’’ of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited Jetstream Series 4100 AMM, Revision 35, dated February 15, 2011: Prior to the accumulation of the applicable flight hours specified in the ‘‘Time Between Checks’’ column in Subject 05–10–20, or within 90 days after November 23, 2011 (the effective date of AD 2011–21– 06, Amendment 39–16829 (76 FR 64788, October 19, 2011), whichever occurs later; except for tasks that specify ‘‘first flight of the day’’ in the ‘‘Time Between Checks’’ column in Subject 05–10–20, the initial compliance time is the first flight of the next day after doing the revision required by paragraph (g) of this AD, or within 90 days after November 23, 2011 (the effective date of AD 2011–21– 06), whichever occurs later.


### 26487 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules

(h) Retained Restrictions on Alternative Actions, Intervals, and/or CDCCLs, With a New Exception

This paragraph restates the requirements of paragraph (k) of AD 2011–21–06, Amendment 39–16829 (76 FR 64788, October 19, 2011), with a new exception. Except as required by paragraph (i) of this AD, after accomplishing the revision required by paragraph (g) of this AD, no alternative actions ( e.g., inspections), intervals, and/or CDCCLs may be used unless the actions, intervals, and/or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (l) of this AD.

(i) New Maintenance or Inspection Program
Revision

Within 90 days after the effective date of this AD: Revise the maintenance or inspection program, as applicable, by incorporating Subjects 05–10–10, ‘‘Airworthiness Limitations’’; 05–10–20, ‘‘Certification Maintenance Requirements’’; and 05–10–30, ‘‘Critical Design Configuration Control Limitations (CDCCL)—Fuel System’’; of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited J41 AMM, Revision 38, dated September 15, 2013. The initial compliance times for the tasks are at the applicable times specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD. Doing the actions required by this paragraph terminates the requirements of paragraph (g) of this AD.

(1) For replacement tasks of life limited parts specified in Subject 05–10–10, ‘‘Airworthiness Limitations,’’ of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited J41 AMM, Revision 38, dated September 15, 2013: Prior to the applicable flight cycles (landings) or flight hours (flying hours) on the part specified in the ‘‘Mandatory Life Limits’’ column in Subject 05–10–10, or within 90 days after the effective date of this AD,
whichever occurs later.

(2) For structurally significant item tasks specified in Subject 05–10–10, ‘‘Airworthiness Limitations,’’ of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited J41 AMM, Revision 38, dated September 15, 2013: Prior to the accumulation of the applicable flight cycles specified in the ‘‘Initial Inspection’’ column in Subject 05–10–10, or within 90 days after the effective date of this AD,
whichever occurs later.

(3) For certification maintenance requirements tasks specified in Subject 05– 10–20, ‘‘Certification Maintenance Requirements,’’ of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited J41 AMM, Revision 38, dated September 15, 2013: Prior to the accumulation of the applicable flight hours specified in the ‘‘Time Between Checks’’ column in Subject 05–10–20, or within 90 days after the effective date of this AD, whichever occurs later; except for tasks that specify ‘‘first flight of the day’’ in the ‘‘Time Between Checks’’ column in Subject 05–10–20, the initial compliance time is the first flight of the next day after doing the revision required by paragraph (j) of this AD, or within 90 days the effective date of this AD, whichever occurs later.

(j) New Restrictions on Alternative Actions, Intervals, and/or (CDCCLs)

After the maintenance or inspection program, as applicable, has been revised as required by paragraph (i) of this AD, no alternative actions ( e.g., inspections), intervals, and/or CDCCLs may be used unless the actions, intervals, and/or CDCCLs are approved as an AMOC in accordance with the procedures specified in paragraph (l) of this AD.

(k) Credit for Previous Actions

This paragraph restates the provisions of paragraph (j) of AD 2011–21–06, Amendment 39–16829 (76 FR 64788, October 19, 2011). This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before November 23, 2011 (the effective date of AD 2011–21–06), in accordance with Subjects 05–10–10, ‘‘Airworthiness Limitations’’; 05–10–20, ‘‘Certification Maintenance Requirements’’; and 05–10–30, ‘‘Critical Design Configuration Control Limitations (CDCCL)—Fuel System’’; of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited Jetstream Series 4100 AMM, Revision 33, dated February 15, 2010; which are not incorporated by reference in this AD.

(l) Other FAA AD Provisions

The following provisions also apply to this

AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1175; fax 425–227–1149. Information may be emailed to: 9-ANM-116- AMOC-REQUESTS@faa.gov.

(i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD.

(ii) AMOCs approved previously for AD 2011–21–06, Amendment 39–16829 (76 FR 64788, October 19, 2011), are not approved as AMOCs with this AD.

(2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or BAE Systems (Operations) Limited’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature.

(m) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0043, dated February 21, 2014, for related information. This MCAI may be found in the AD docket
on the Internet at http://www.regulations.gov by searching for and locating Docket No.

FAA–2015–1279.

(2) For service information identified in this AD, contact BAE SYSTEMS (Operations) Limited, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email RApublications@ baesystems.com ; Internet http:// www.baesystems.com/Businesses/ RegionalAircraft/index.htm . You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

Issued in Renton, Washington, on April 29,

2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–11023 Filed 5–7–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–1277; Directorate Identifier 2014–NM–155–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This proposed AD was prompted by fatigue testing that determined fatigue damage could appear on clips, shear webs, and angles at certain rear fuselage sections and certain frames. This proposed AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This proposed AD would require replacing the clips, the shear webs, and angles, including doing all applicable related investigative